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Iodine Hall Thruster Propellant Feed System for a CubeSatThe components required for an in-space iodine vapor-fed Hall effect thruster propellant management system are described. A laboratory apparatus was assembled and used to produce iodine vapor and control the flow through the application of heating to the propellant reservoir and through the adjustment of the opening in a proportional flow control valve. Changing of the reservoir temperature altered the flowrate on the timescale of minutes while adjustment of the proportional flow control valve changed the flowrate immediately without an overshoot or undershoot in flowrate with the requisite recovery time associated with thermal control systems. The flowrates tested spanned a range from 0-1.5 mg/s of iodine, which is sufficient to feed a 200-W Hall effect thruster.
Document ID
20140012577
Acquisition Source
Marshall Space Flight Center
Document Type
Conference Paper
Authors
Polzin, Kurt A. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Peeples, Steven (NASA Marshall Space Flight Center Huntsville, AL, United States)
Date Acquired
September 25, 2014
Publication Date
July 28, 2014
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
M14-3863
Report Number: M14-3863
Meeting Information
Meeting: AIAA/ASME/SAE/ASEE Joint Propulsion Conference
Location: Cleveland, OH
Country: United States
Start Date: July 28, 2014
End Date: July 30, 2014
Sponsors: American Inst. of Aeronautics and Astronautics, Society of Automotive Engineers, Inc., American Society for Electrical Engineers, American Society of Mechanical Engineers
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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